A method for determining the transfer orbit of a lunar probe

A technology for transferring orbits and detectors, applied in the field of spacecraft dynamics research, can solve problems such as incomplete force models, inability to obtain high precision, and inability to obtain GNSS data support, etc., to achieve the effect of improving the progress of orbit calculations
CN104914458BActive Publication Date: 2017-07-04CHINA XIAN SATELLITE CONTROL CENT
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
CHINA XIAN SATELLITE CONTROL CENT
Publication Date
2017-07-04

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Abstract

The invention provides a method for determining the transfer orbit of the lunar probe, which is based on the establishment of a force model at the time of separation between the lunar probe and the ket, combined with the high-precision global satellite navigation and positioning data before and after the separation of the ket, and solving the pre-separation and the orbital parameters of the ket after separation; then, using the law of conservation of momentum, the separation force between the lunar probe and the ket at the time of separation, and the instantaneous space attitude of the ket (the direction of the separation force) are solved; finally, the calculation of the orbital transfer orbit of the lunar probe at the launch stage is obtained result. The invention can obtain a relatively high-precision lunar probe into the transfer orbit, and provide a relatively high-precision initial orbit for the subsequent midway correction of the lunar probe.
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Description

technical field

[0001] The invention belongs to the field of spacecraft dynamics research, and in particular relates to a method for determining the launch orbit of a lunar probe. Background technique

[0002] The launch of the lunar probe into the transfer orbit is the first space orbit for the probe to transfer to the moon and rendezvous with it after the probe is separated from the final stage of the launch vehicle. The starting point is usually represented by orbital epochs, position and velocity in the inertial coordinate system, or by orbital epochs and Kepler orbital elements. The Lunar Probe Measurement and Control Center can obtain the space trajectory of the Lunar Probe flying to the Moon over time based on the determination results of the injection transfer orbit.

[0003] For the determination of the traditional lunar probe's launch and transfer orbit, the measurement data comes from the ground radar tracking and measurement system, relying on the ground radar s...

Claims

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